摘要
霍尔推力器的热设计对磁场性能有显著影响。为研究推力器的热优化方法,对典型霍尔推力器进行热分布计算。采用热传导与热辐射耦合的计算方法,以辐射传递系数替代角系数,来表征微元表面间的相对位置对热辐射的影响。为验证模型及相关经验参数的正确性,在真空舱中开展推力器试验件的放电试验,获得推力器外部4个测点的温度,并以此结果与同结构、同工况下的计算数据进行比对,模型的最大相对误差可以控制在10%以内。在此基础上,考察了几种典型的热设计方法对导磁组件温度分布的影响,接着,对最优方案进行磁场性能变化的评估。本文结果可对霍尔推力器的热设计优化提供参考。
The temperature distribution in typical Hall thruster was mathematically modeled,theoretically analyzed in the coupled algorithmof heat conduction and radiation,numerically simulated and experimentally evaluatedin the lab-built thruster discharge test platform for thermal design optimization. The influence of the relative positionsof the micro-surfaces,including the cooling-fin and anode support,on the radiation transfer was described more precisely with the radiation transfer coefficient instead of the angular coefficient. The simulation model was repeatedly modified on the basis of the measurement under the same operating conditions and with the same thruster structure till the largest relative discrepancy between the measured and simulated results below 10%. In addition,the impact of the newly-developed thermal design schemes on the temperature profile of the permeability magnetic assemblies was investigated to improve the magnetic field performance. We suggest that the novel thermal design optimization may be of some technological interest.
出处
《真空科学与技术学报》
EI
CAS
CSCD
北大核心
2018年第2期150-156,共7页
Chinese Journal of Vacuum Science and Technology
关键词
霍尔推力器
数值分析
辐射传递系数
热设计优化
Hall thruster, Numerical analysis, Radiation transfer coefficient, Optimization of the thermal per-formance
